@inproceedings{oai:jaxa.repo.nii.ac.jp:00004251,
 author = {青野, 淳也 and 葛生, 和人 and Aono, Junya and Kuzuu, Kazuto},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012},
 month = {Mar},
 note = {第44回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県, 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan, The overset grid approach provides a very powerful means of handling complex geometries in computational fluid dynamics. The overset grid approach has many practical benefits for unsteady moving grid simulation or rudder angle. Therefore an overset unstructured grid method was newly developed for an arbitrary polyhedral compressible flow solver, LS-FLOW. We set the IBlank for visualization and post-processing. In order to test the validity of the suggested methods, a numerical simulation was carried out on the NACA0012 airfoil.And our results are compared with experimental data and other CFD results. Furthermore, in order to evaluate the validity of this method, we also simulated the flow around a reusable sounding rocket under research at JAXA//ISAS. The result of the overset grid method corresponds with the result of the single grid method in the NACA0012 airfoil and the reusable sounding rocket. The good coincidence validates our newly deve""" loped overset grid method, and intend to use LS-FLOW as a design tool., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061958011, レポート番号: JAXA-SP-12-010},
 pages = {61--66},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {任意多面体非構造圧縮性ソルバーLS-FLOWにおける重合格子法開発},
 volume = {JAXA-SP-12-010},
 year = {2013}
}